Virtual Instrument-based Signal Acquisition And Control System Development

The research about aircraft Integrated Modular Avionics system needs system emulation. The Avionics & simulation lab not only a the platform of the testing & verification about Avionics design, but also is a absolutely necessarily tool and instrumentality in each phase of support & maintain for the development of airborne software & subsystem, system integration and the support of project flight-fly. From emulation examination, it can be short greatly the period of the Avionics system research and reduce the cost.As the main part of laboratory, avionic simulation facility is a software and hardware system which is very complex. Operation and control process of facility requires a large amount of data as the input/output condition, and data acquisition/control is an important component part indispensable for the facility. this thesis is to develop a set of acquisition and control system for avionic simulation laboratory research of one aircraft type .This thesis elaborates elementary theory of data acquisition as well as concept & characteristic of Virtual Instrument technology, introduced the form of avionics simulation lab, then performs detailed demand analysis for the research object of this study subject, and conducts design of hardware and software. In the part of hardware design, considering factors such as feasibility of hardware implementation, development cycle, reliability and price, it is determined that hardware scheme of data acquisition control system is scheme of data acquisition board card (DAQ) based on PC bus, and research is also performed for model selection and connecting type of master-control computer, data acquisition card, signal conditioning, etc. Finally, hardware platform of acquisition control system is constructed. In the part of software design, it has explored for implementation approach of software, establishing the software development method combining two development tools of LabWindows/CVI8.0 and Visual C++6.0, to make the use of the each characteristic of these two tools. Software design adopts a design method which is hierarchical and modularized, and minimizes coupling between modules, allowing for clarity, expandability and strong readability of program structure. Using configuration files on hardware resource and tested signal made the software be provided with definite universal.This thesis realizes acquisition and drive to multi-type data about simulated cockpit and each subsystem in Avionics,"Emulational Switch"function achieved, it also could support system examination without simulated cockpit, presented a set of convenient and friendly man-machine interface (virtual panel) for the end user-Avionics system designer and airborne software developer.By the testing and verification of practical application, the system operates stably. Its reality, reliability and stability can completely meet application requirement of avionic system experiment, and the purpose of this study subject is achieved.